EP3139000B1 - Goupille amortissante pour amortir des aubes de turbine adjacentes couplées à un arbre de rotor et moteur à turbine - Google Patents

Goupille amortissante pour amortir des aubes de turbine adjacentes couplées à un arbre de rotor et moteur à turbine Download PDF

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Publication number
EP3139000B1
EP3139000B1 EP16184881.7A EP16184881A EP3139000B1 EP 3139000 B1 EP3139000 B1 EP 3139000B1 EP 16184881 A EP16184881 A EP 16184881A EP 3139000 B1 EP3139000 B1 EP 3139000B1
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EP
European Patent Office
Prior art keywords
end portion
damper pin
pin
turbine
damper
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16184881.7A
Other languages
German (de)
English (en)
Other versions
EP3139000A1 (fr
Inventor
Spencer A. KAREFF
Brian Denve POTTER
Ariel Caesar Prepena Jacala
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
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General Electric Technology GmbH
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Publication date
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Publication of EP3139000A1 publication Critical patent/EP3139000A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention generally relates to a turbomachine having multiple circumferentially aligned turbine blades. More precisely, the present invention relates to a damper pin for damping adjacent turbine blades coupled to a rotor shaft, and also relates to a turbine engine. More particularly, this invention involves a damper pin having a spring member for providing vibration damping between adjacent turbine blades.
  • a turbine blade also known as a turbine bucket or turbine rotor blade, converts energy from a flowing fluid such as hot combustion gas or steam into mechanical energy by causing a rotor shaft of a turbomachine to rotate. As the turbomachine transitions through various operating modes, the turbine blades are subjected to both mechanical and thermal stresses.
  • a turbine blade generally includes an airfoil that extends radially outwardly from a platform, a shank that extends radially inwardly from the platform and a dovetail or mounting portion that extends radially inwardly from the shank.
  • the dovetail of each turbine blade is secured within a complementary slot defined in a rotor wheel or disk.
  • the rotor wheel is coupled to the rotor shaft.
  • vibrations may be introduced into the turbine blades. For example, fluctuations in flow of the hot combustion gases or steam may cause them to vibrate.
  • One basic design consideration for turbomachine designers is to avoid or to minimize resonance with natural frequencies of the turbine blades and the dynamic stresses produced by forced response and/or aero-elastic instabilities, thus controlling high cycle fatigue of the turbine blades.
  • vibration dampers are typically provided below and/or between the platforms to frictionally dissipate vibratory energy and reduce the corresponding amplitude of vibration during operation.
  • the amount of vibrational energy that is removed by the vibration damper is a function of the dynamic weight of the vibration damper and the reaction loads.
  • US 2912223 discloses a turbine bucket vibration dampener.
  • dampers may be largely adequate during typical operations, there is a desire to improve overall damper effectiveness.
  • Prior attempts to accomplish damping of vibrations have included round damper pins, sheet metal flat dampers, or complex wedge shaped dampers. Often true damper performance of these types of dampers is not known until the first engine test. However, at that time, the damper pocket geometry in the turbine blades is locked in by hard tooling. Thus, if the damper does not perform as expected, then a potentially expensive tooling rework may be required. Accordingly, there is desire for a damping pin that provides a natural frequency tuning tool for resonant mode excitation avoidance and that enables independent mode tuning options without necessitating changes to the design of an existing turbine blade.
  • One embodiment of the present invention is a damper pin according to claim 1.
  • Another embodiment of the present invention is a turbine engine according to claim 10.
  • upstream and downstream refer to the relative direction with respect to fluid flow in a fluid pathway.
  • upstream refers to the direction from which the fluid flows
  • downstream refers to the direction to which the fluid flows.
  • radially refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component
  • axially refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component.
  • the present invention as shown and described herein is not limited to a land based and/or industrial gas turbine unless otherwise specified in the claims.
  • the invention as described herein may be used in any type of turbomachine including but not limited to a steam turbine, an aircraft gas turbine or marine gas turbine.
  • FIG. 1 illustrates a schematic diagram of one embodiment of a gas turbine 10.
  • the gas turbine 10 generally includes an inlet section 12, a compressor section 14 disposed downstream of the inlet section 12, a plurality of combustors (not shown) within a combustor section 16 disposed downstream of the compressor section 14, a turbine section 18 disposed downstream of the combustor section 16 and an exhaust section 20 disposed downstream of the turbine section 18. Additionally, the gas turbine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.
  • the turbine section 18 may generally include a rotor shaft 24 having a plurality of rotor disks 26 (one of which is shown) and a plurality of rotor blades 28 extending radially outwardly from and being interconnected to the rotor disk 26. Each rotor disk 26 in turn, may be coupled to a portion of the rotor shaft 24 that extends through the turbine section 18.
  • the turbine section 18 further includes an outer casing 30 that circumferentially surrounds the rotor shaft 24 and the rotor blades 28, thereby at least partially defining a hot gas path 32 through the turbine section 18.
  • a working fluid such as air flows through the inlet section 12 and into the compressor section 14 where the air is progressively compressed, thus providing pressurized air to the combustors of the combustion section 16.
  • the pressurized air is mixed with fuel and burned within each combustor to produce combustion gases 34.
  • the combustion gases 34 flow through the hot gas path 32 from the combustor section 16 into the turbine section 18, wherein energy (kinetic and/or thermal) is transferred from the combustion gases 34 to the rotor blades 28, thus causing the rotor shaft 24 to rotate.
  • the mechanical rotational energy may then be used to power the compressor section 14 and/or to generate electricity.
  • the combustion gases 34 exiting the turbine section 18 may then be exhausted from the gas turbine 10 via the exhaust section 20.
  • FIG. 2 illustrates a conventional turbine blade or bucket 28 including an airfoil 36, a platform 38, a shank 40 and a dovetail or mounting portion 42.
  • FIG. 3 provides a downstream view of a pair of circumferentially adjacent turbine blades 28(a), 28(b).
  • the dovetail 42 is utilized to secure the turbine blade 28 to a periphery of the rotor disk 26 ( FIG. 1 ), as is well understood in the art.
  • the platform 38 defines an inward flow boundary for the combustion gases 34 flowing through the hot gas path 32 of the turbine section 18 ( FIG. 1 ).
  • a damper pin 44 is located along one axial edge (or slash face) 46 adjacent to (i.e., radially inward of) the turbine blade platform 38. It will be appreciated that a similar damper pin 44 is located between each adjacent pair of turbine blades 28(a), 28(b) ( FIG. 3 ) on the rotor disk 26 ( FIG. 1 ) as apparent from FIG. 3 . In particular embodiments, as shown in FIG. 2 , the damper pin 44 is located in an elongated groove 48 ( FIG. 1 ) that extends along the entire slash face 46 of the turbine blade 28.
  • the damper pin 44 serves as a vibration damper. When installed, as shown in FIG. 3 , the damper pin 44 is positioned between the adjacent turbine blades 28(a), 28(b). In operation, the damper pin 44 frictionally dissipates vibratory energy and reduces corresponding amplitude of vibration. The amount of vibrational energy that is removed by the damper pin 44 is a function several factors including but not limited to the dynamic weight of the damper pin 44, the geometry of the damper pin 44 and the reaction loads between the adjacent turbine blades 28(a), 28(b).
  • FIG. 4 provides a side view of a comparative example of a damper pin 100.
  • FIG. 5 provides a top view of the damper pin 100 as shown in FIG. 4 . It is to be understood that damper pin 100 shown in FIG. 4 may be substituted for damper pin 44 as shown in FIGS. 2 and 3 , as a comparative example not according to the invention.
  • the damper pin 100 includes a first end portion 102 axially spaced from a second end portion 104 with respect to an axial centerline 106 of the damper pin 100.
  • the first end portion 102 and the second end portion 104 may be coaxially aligned with respect to centerline 106.
  • the damper pin 100 further includes a spring member 108 that extends axially from an inner surface 110 of the first end portion 102 to an inner surface 112 of the second end portion 104.
  • the first end portion 102, the spring member 108 and the second end portion 104 define a generally arcuate top portion or surface 114 of the damper pin 100.
  • the top portion 114 is generally configured (shaped and/or sized) to contact with a portion of the groove 48 defined between the adjacent turbine blades 28(a), 28(b).
  • the first end portion 102 and/or the second end portion 104 of the damper pin 100 are substantially semi-cylindrical. As shown in FIG. 4 , the first end portion 102 and/or the second end portion 104 may include shoulders 116, 118 respectively. This configuration creates flat support surfaces 120, 122 that are adapted to rest on machined turbine blade platform surfaces or shoulders at opposite ends of the groove 48 formed in the turbine blade slash face 46, thereby providing support for the damper pin 100 while preventing undesirable excessive rotation during machine operation.
  • opposing ends 124, 126 of the spring member 108 may be fixedly connected to the first end portion 102 and the second end portion 104 respectively.
  • the opposing ends 124, 126 of the spring member 108 may be engaged with or compressed against the inner surface 110 of the first end portion 102 and/or the inner surface 112 of the second end portion 104.
  • the spring member 108 is generally helical shaped. Although the spring member is illustrated in the figures as a helical or coil type spring, it is to be understood by one skilled in the art that the spring member 108 may be any suitable type spring such as but not limited to a wave spring or the like and that the invention is not limited to a helical or coil type spring member unless otherwise provided in the claims.
  • the spring member 108 may comprise multiple springs coaxially aligned and extending between the first end portion 102 and the second end portion 104.
  • the spring member 108 comprises a first spring 128 coaxially aligned with a second spring 130.
  • the first spring 128 may be connected at one end 132 to the first end portion 102 and the second spring 130 may be connected at one end 134 to the second end portion 104.
  • the first and second springs 128, 130 may be engaged at contact point 136 that is defined between the inner surface 110 of the first end portion 102 and the inner surface 112 of the second end portion 104.
  • FIG. 6 is a cross sectional side view of an exemplary embodiment of the damper pin 100 according to one embodiment of the present invention.
  • the damper pin 100 includes a retention pin 138.
  • the retention pin 138 is coaxially aligned with and disposed between the first end portion 102 and the second end portion 104.
  • the spring member 108 extends circumferentially around the retention pin 138.
  • the retention pin 138 may be seated within openings 140(a), 140(b) defined by the first end portion 102 and the second end portion 104 respectively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Goupille d'amortisseur (100) permettant d'amortir des aubes de turbine adjacentes accouplées à un arbre de rotor (24), la goupille d'amortisseur (100) comprenant :
    une première partie d'extrémité (102) alignée axialement avec et espacée axialement d'une seconde partie d'extrémité (104) ;
    un élément de ressort (108) qui s'étend axialement d'une surface interne de la première partie d'extrémité (102) à une surface interne de la seconde partie d'extrémité (104), dans laquelle la première partie d'extrémité (102), l'élément de ressort (108) et la seconde partie d'extrémité (104) définissent une partie supérieure généralement arquée (114) de la goupille d'amortisseur (100) conçue pour être disposée à l'intérieur d'une rainure (48) définie entre les aubes de turbine adjacentes et pour entrer en contact avec la rainure (48) ;
    caractérisée en ce que la goupille d'amortisseur (100) comprend en outre une goupille de retenue (138) alignée coaxialement avec et disposée entre la première partie d'extrémité (102) et la seconde partie d'extrémité (104), dans laquelle l'élément de ressort (108) s'étend circonférentiellement autour de la goupille de retenue (138).
  2. Goupille d'amortisseur (100) selon la revendication 1, dans laquelle l'élément de ressort (108) est de forme hélicoïdale.
  3. Goupille d'amortisseur (100) selon la revendication 1 ou 2, dans laquelle l'élément de ressort (108) est relié à au moins l'une parmi la surface interne de la première partie d'extrémité (102) ou la surface interne de la seconde partie d'extrémité (104).
  4. Goupille d'amortisseur (100) selon la revendication 1, 2 ou 3, dans laquelle l'élément de ressort (108) comprend un premier ressort (128) et un second ressort (130), et dans laquelle le premier ressort (128) est aligné coaxialement avec le second ressort (130).
  5. Goupille d'amortisseur (100) selon la revendication 4, dans laquelle le premier ressort (128) est relié au niveau d'une extrémité de la première partie d'extrémité (102) et le second ressort (130) est relié au niveau d'une extrémité de la seconde partie d'extrémité (104).
  6. Goupille d'amortisseur (100) selon l'une quelconque revendication précédente, dans laquelle la goupille de retenue (138) est logée à l'intérieur d'une ouverture (140a) définie par la première partie d'extrémité (102).
  7. Goupille d'amortisseur (100) selon l'une quelconque revendication précédente, dans laquelle la goupille de retenue (138) est logée à l'intérieur d'une ouverture (140b) définie par la seconde partie d'extrémité (104).
  8. Goupille d'amortisseur (100) selon l'une quelconque revendication précédente, dans laquelle une partie de la première partie d'extrémité (102) est semi-cylindrique.
  9. Goupille d'amortisseur (100) selon l'une quelconque revendication précédente, dans laquelle une partie de la seconde partie d'extrémité (104) est semi-cylindrique.
  10. Moteur à turbine (10), comprenant :
    un arbre de rotor (24) qui s'étend axialement à l'intérieur du moteur à turbine (10) ;
    une paire adjacente d'aubes de turbine accouplées à l'arbre de rotor (24), chaque aube de turbine de ladite paire adjacente d'aubes de turbine définissant au moins partiellement une rainure (48) qui s'étend le long d'une face oblique (46) de ladite chaque aube de turbine ; et
    une goupille d'amortisseur (100) selon l'une quelconque revendication précédente, disposée à l'intérieur de la rainure (48) et en contact avec la rainure (48).
EP16184881.7A 2015-09-03 2016-08-19 Goupille amortissante pour amortir des aubes de turbine adjacentes couplées à un arbre de rotor et moteur à turbine Active EP3139000B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/844,317 US10385701B2 (en) 2015-09-03 2015-09-03 Damper pin for a turbine blade

Publications (2)

Publication Number Publication Date
EP3139000A1 EP3139000A1 (fr) 2017-03-08
EP3139000B1 true EP3139000B1 (fr) 2023-12-13

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EP16184881.7A Active EP3139000B1 (fr) 2015-09-03 2016-08-19 Goupille amortissante pour amortir des aubes de turbine adjacentes couplées à un arbre de rotor et moteur à turbine

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US (1) US10385701B2 (fr)
EP (1) EP3139000B1 (fr)
JP (1) JP6827736B2 (fr)
CN (1) CN106499445B (fr)

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US10648347B2 (en) * 2017-01-03 2020-05-12 General Electric Company Damping inserts and methods for shrouded turbine blades
JP7039355B2 (ja) * 2018-03-28 2022-03-22 三菱重工業株式会社 回転機械
US11187089B2 (en) * 2019-12-10 2021-11-30 General Electric Company Damper stacks for turbomachine rotor blades
US11248475B2 (en) 2019-12-10 2022-02-15 General Electric Company Damper stacks for turbomachine rotor blades
US11242756B2 (en) 2020-05-04 2022-02-08 General Electric Company Damping coating with a constraint layer
US11333026B2 (en) 2020-05-26 2022-05-17 General Electric Company Vibration-damping system for turbomachine blade(s) on spacer adjacent blade stage
US11085303B1 (en) 2020-06-16 2021-08-10 General Electric Company Pressurized damping fluid injection for damping turbine blade vibration
US11143036B1 (en) 2020-08-20 2021-10-12 General Electric Company Turbine blade with friction and impact vibration damping elements
US11208903B1 (en) * 2020-11-20 2021-12-28 Solar Turbines Incorporated Stiffness coupling and vibration damping for turbine blade shroud

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US2912223A (en) * 1955-03-17 1959-11-10 Gen Electric Turbine bucket vibration dampener and sealing assembly
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
CH418360A (de) * 1962-11-21 1966-08-15 Ass Elect Ind Turbomaschine
EP3043085A1 (fr) * 2015-01-08 2016-07-13 Siemens Aktiengesellschaft Agencement d'aubes pour une turbo-machine thermique à flux axial et procédé de montage d'un élément amortisseur entre deux aubes d'une couronne d'aube d'une turbo-machine thermique

Also Published As

Publication number Publication date
JP2017048788A (ja) 2017-03-09
CN106499445A (zh) 2017-03-15
US10385701B2 (en) 2019-08-20
CN106499445B (zh) 2020-04-24
JP6827736B2 (ja) 2021-02-10
US20170067348A1 (en) 2017-03-09
EP3139000A1 (fr) 2017-03-08

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